US3755963A - Actuator for a rudder of model plane - Google Patents

Actuator for a rudder of model plane Download PDF

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Publication number
US3755963A
US3755963A US00205894A US3755963DA US3755963A US 3755963 A US3755963 A US 3755963A US 00205894 A US00205894 A US 00205894A US 3755963D A US3755963D A US 3755963DA US 3755963 A US3755963 A US 3755963A
Authority
US
United States
Prior art keywords
rudder
disc
yokes
actuator
model plane
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US00205894A
Other languages
English (en)
Inventor
K Mabuchi
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mabuchi Motor Co Ltd
Original Assignee
Mabuchi Motor Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Mabuchi Motor Co Ltd filed Critical Mabuchi Motor Co Ltd
Application granted granted Critical
Publication of US3755963A publication Critical patent/US3755963A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • A—HUMAN NECESSITIES
    • A63—SPORTS; GAMES; AMUSEMENTS
    • A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
    • A63H27/00—Toy aircraft; Other flying toys
    • A63H27/02—Model aircraft

Definitions

  • An actuator for a rudder of a model plane comprises a pair of arched yokes opposingly arranged around the periphery of a permanent magnet of disc form.
  • An electromagnet having windings for separately magnetizing each of the yokes is provided.
  • An actuating lever is secured, at its one end, to a shaft of the permanent magnet disc and a rudder of a vertical tail of the model plane is coupled to the other end 011 the actuating lever through an appropriate link mechanism.
  • the present invention relates to an actuator for a rudder of a model plane, and more particularly to an actuator for tilting the rudder of a vertical tail of a model plane rightward or leftward through a wireless control means during the flight of the model plane which is adapted to fly by a drive motor such as a miniature electric motor, gasoline engine or the like under wireless control system.
  • a drive motor such as a miniature electric motor, gasoline engine or the like under wireless control system.
  • an actuator for a rudder of a model plane under wireless control system comprising a permanent magnet of disc form, a pair of arched yokes opposingly arranged around the periphery of the permanent magnet disc, an electromagnet having windings for separately magnetizing each of said yokes, an actuating lever secured, at its one end, to a shaft of said permanent magnet disc, and a rudder of a vertical tail of the model plane coupled to the other end of said actuating lever through a link mechanism.
  • Numeral 1 represents a board made of non-magnetic materials, numeral 2 a permanent magnet of disc form, numeral 3 an actuating lever, numeral 4 a vertical tail, numeral 4a a rudder and numeral 5 a control lever.
  • the non-magnetic board 1 is appropriately mounted within the body of the model airplane adjacent the tail thereof.
  • a shaft 2a is f xedly secured, which shaft 2a is rotatably fitted to the insulator 1.
  • the actuating lever 3 is operatively connected to the rudder 4a through any conventional linkage mechanism, for example, as illustrated in U. S. Pat. No. 3,699,708.
  • the control lever 5 is fixedly secured to the front end of the shaft 2a and adapted to rotate clockwise or counterclockwise by rotation angle defined by stop elements la and 1b protruding from the non-magnetic board 1.
  • the control lever 5 and the actuating lever 3 may be formed integrally with each other.
  • the bobbin 6 is appropriately mounted within the body of the model airplane in the same manner as the other components thereof, as, for example, as illustrated in U. S. Pat. No. 3,699,708.
  • An electromagnet is formed of windings 7 and the bobbin 6. Lead wires 7a, 7b and 7c are taken out through one side plate of the bobbin 6.
  • Yokes 8 and 9 are arranged around the outer periphery of the permanent magnet 2 of disc form, leaving a desired gap therebetween.
  • the yokes 8 and 9 are secured to the opposite side plates of the bobbin 6 through magnetic plates 8a and 90, respectively.
  • a switching means (not shown) of conventional design well known in the prior art having two contacts connected to the windings of the electromagnet through the lead wires, and 7c, and also a neutral position.
  • a fixed contact of the switching means is connected to the positive'terrninal of a power source also suitably mounted within the model airplane in conventional manner.
  • the lead wires 7a and 7c are further connected through windings to the lead wire 7b which is in turn connected to a negative terminal of the power source.
  • S aid switching means is adapted to operate under a remote control system.
  • the rudder 4a of the vertical tail 4 is held in a predetermined position.
  • the switch is closed and a current is applied through the lead wires 7a and 7b the actuating lever 3 is rotated to the left, i.e., in the direction indicated by arrow L, by the action of the yoke 8 and the pennanent magnet disc 2.
  • the rudder 4a of the vertical tail 4 is turned to the left.
  • the switch is closed to apply a current through the lead wires 7c and 7b
  • the actuating lever 3 is rotated in the opposite direction, i.e., to the right as shown by arrow R.
  • a pair of arched yokes are opposingly arranged around the periphery of the permanent magnet disc; the permanent magnet disc is caused to rotate clockwise or counterclockwise by the selection of electrical path to the windings; and the actuating lever for actuating the rudder is secured to the shaft of the permanent magnet; thereby to make the actuator of the present invention simple in structure light in weight and positive and reliable in operation, lowering the manufacturing cost, and saving the space to be occupied by the actuator.
  • the actuator of the present invention is made just suitable for a rudder of a model plane.
  • a system for actuating the rudder comprising:

Landscapes

  • Toys (AREA)
US00205894A 1970-12-08 1971-12-08 Actuator for a rudder of model plane Expired - Lifetime US3755963A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP1970121677U JPS5215353Y1 (enrdf_load_stackoverflow) 1970-12-08 1970-12-08

Publications (1)

Publication Number Publication Date
US3755963A true US3755963A (en) 1973-09-04

Family

ID=14817133

Family Applications (1)

Application Number Title Priority Date Filing Date
US00205894A Expired - Lifetime US3755963A (en) 1970-12-08 1971-12-08 Actuator for a rudder of model plane

Country Status (7)

Country Link
US (1) US3755963A (enrdf_load_stackoverflow)
JP (1) JPS5215353Y1 (enrdf_load_stackoverflow)
AU (1) AU467538B2 (enrdf_load_stackoverflow)
CA (1) CA966659A (enrdf_load_stackoverflow)
DE (1) DE2160658A1 (enrdf_load_stackoverflow)
FR (1) FR2117547A5 (enrdf_load_stackoverflow)
GB (1) GB1368290A (enrdf_load_stackoverflow)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060144995A1 (en) * 2004-12-10 2006-07-06 Clancy Andy J Remotely controlled model airplane having deflectable centrally biased control surface

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR890001452Y1 (ko) * 1986-06-19 1989-04-05 삼성물산 주식회사 완구의 부품 분리장치

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2277378A (en) * 1938-07-30 1942-03-24 Boeing Aircraft Co Power means for operating aircraft control surfaces
US2671863A (en) * 1951-01-24 1954-03-09 Milwaukee Gas Specialty Co Electromagnetic control device
US2771572A (en) * 1953-11-16 1956-11-20 Frank R Adams Polarized self-neutralizing servomotor
US2903822A (en) * 1955-07-08 1959-09-15 Donald V Reid Radio controlled model submarine
US3152290A (en) * 1962-06-06 1964-10-06 Gen Motors Corp Rotary electromagnet construction
US3355838A (en) * 1965-06-17 1967-12-05 Ronald E Huffman Fluid pressure control for model aircraft

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2277378A (en) * 1938-07-30 1942-03-24 Boeing Aircraft Co Power means for operating aircraft control surfaces
US2671863A (en) * 1951-01-24 1954-03-09 Milwaukee Gas Specialty Co Electromagnetic control device
US2771572A (en) * 1953-11-16 1956-11-20 Frank R Adams Polarized self-neutralizing servomotor
US2903822A (en) * 1955-07-08 1959-09-15 Donald V Reid Radio controlled model submarine
US3152290A (en) * 1962-06-06 1964-10-06 Gen Motors Corp Rotary electromagnet construction
US3355838A (en) * 1965-06-17 1967-12-05 Ronald E Huffman Fluid pressure control for model aircraft

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060144995A1 (en) * 2004-12-10 2006-07-06 Clancy Andy J Remotely controlled model airplane having deflectable centrally biased control surface
US7121506B2 (en) * 2004-12-10 2006-10-17 Clancy Andy J Remotely controlled model airplane having deflectable centrally biased control surface

Also Published As

Publication number Publication date
AU467538B2 (en) 1975-12-04
FR2117547A5 (enrdf_load_stackoverflow) 1972-07-21
GB1368290A (en) 1974-09-25
JPS5215353Y1 (enrdf_load_stackoverflow) 1977-04-06
AU3654071A (en) 1973-06-14
CA966659A (en) 1975-04-29
DE2160658A1 (de) 1972-06-29

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